BEng (Hons) Aerospace Engineering
AE3110 AEROSPACE TECHNOLOGY
THE DEVELOPMENT OF MODERN TRANSPORT AIRCRAFT.
10th January 2007
TABLE OF CONTENTS
1 INTRODUCTION 1
2 Key Performance Constraints 2
2.1 Balanced Field Length. 2
2.2 Landing Distance 5
2.3 Climb and Cruise Requirements. 7
3 Summary 9
4 Conclusion 10
5 Bibliography 11
6 Appendix A Technical Data. 12
7 Appendix B : Thrust/weight—Wing loading selection 13
8 Appendix C 14
(word count – 1565 not including table of contents and headings and appendices)
Introduction
The design of modern civil jet aircraft is always a trade off between different parameters or factors. Thrust to weight ratio and wing loading are two of these key parameters and are interdependent upon each other. That is to say that the amount of wing area available will effect the choice of engine size which will impact on thrust available and thus effect empty weight, fuel weight and therefore maximum all up weight. When considering a new aircraft design these parameters will be affected by decisions on, the range over which the platform will be required to operate competitively. Also the envisaged landing field length will need to be taken into account both for landing distance calculations, as well as the balanced field length for take off calculations. The climb gradient is also an important consideration and indeed these particular characteristics are governed by airworthiness regulations under EASA rules. This specifies that an aircraft should be able to maintain a specified climb angle after a single engine failure. There is also a requirement to make an informed estimation of the cruise thrust that will be necessary to achieve the EASA safety regulations and efficiency requirements which will have range and payload implications.
Key Performance Constraints
1 Balanced Field Length.
The larger the wing area the more air will flow over it and thus more...